CN105447266A - Supportability analysis based FMEA method - Google Patents
Supportability analysis based FMEA method Download PDFInfo
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Abstract
The invention discloses a supportability analysis based FMEA method. The supportability analysis based FMEA method comprises: step 1, performing multilayer decomposition on an initial stipulated layer and making a structural layer diagram from the initial stipulated layer to a lowest stipulated layer; step 2, endowing units corresponding to the initial stipulated layer, each stipulated layer and the lowest stipulated layer in the structural layer diagram with function and performance requirement types; step 3, analyzing functional failures that can be caused by the function and performance requirement types corresponding to the units in the initial stipulated layer, each stipulated layer and the lowest stipulated layer; step 4, forming a plurality of functional failure hardware matrix diagrams; and step 5, analyzing failure reasons and failure influences of the units in the structural layer diagram. With the adoption of the method, the problem in the prior art that a functional failure mode and a corresponding failure reason are easily omitted for a system with relatively large amounts of layers in an actual analysis process can be solved.
Description
Technical field
The present invention relates to aeronautical product experimental technique field, particularly relate to the analytical approach of a kind of FMEA of supportability Analysis and the FMEA analytic system of supportability Analysis.
Background technology
When carrying out the maintenance analysis centered by reliability (RCMA), needing with the fault mode of critical function product (being generally system or subsystem) and reason is input, when carrying out corrective maintenance analysis, need with the fault mode of system/subsystem level and fault detection method for input, therefore need to carry out FMEA, with acquisition system or all possible fault mode of subsystem and each reason causing fault mode, and determine the detection method of each fault mode.
GJB/Z1391-2006 " fault mode, impact and HAZAN guide " in give the analytical approach of FMEA, comprise the method for function FMEA and hardware FMEA, wherein function FMEA is top-down analytical approach, hardware FMEA is analytical approach from bottom to top, but do not set up contact and the corresponding relation of these two kinds of analytical approachs in this standard, easily omit the failure cause of functional fault pattern and correspondence for the system that level is many in actual analysis process, and be not easy when verifying to find to omit, that causes RCMA and corrective maintenance to analyze is imperfect.
Therefore, wish a kind of technical scheme to overcome or at least alleviate at least one above-mentioned defect of prior art.
Summary of the invention
The object of the present invention is to provide the analytical approach of a kind of FMEA of supportability Analysis to overcome or at least alleviate at least one the above-mentioned defect in prior art.
For achieving the above object, the invention provides the analytical approach of a kind of FMEA of supportability Analysis, the analytical approach of the FMEA of described supportability Analysis comprises: step 1: equipment to be analyzed is called initial indenture level, this initial indenture level is carried out multilayer decomposition, form multilayer indenture level, and bottom indenture level is called minimum indenture level, produce the layer of structure figure to minimum indenture level from initial indenture level simultaneously, and by each indenture level in layer of structure figure and each minimum indenture level numbering; Wherein, all have in each indenture level and minimum indenture level multiple equipment to be analyzed decompose after unit; Step 2: function and the performance requirement kind of enumerating described equipment to be analyzed, and function and the performance requirement kind of giving the corresponding unit of the initial indenture level in the layer of structure figure in described step 1, each layer indenture level and minimum indenture level; Step 3: analysis sequence is: from initial indenture level, and go forward one by one to minimum indenture level, analyze the functional fault that the function corresponding to each unit in initial indenture level, each layer indenture level and minimum indenture level and performance requirement kind can occur respectively; Step 4: the layer of structure figure in described step 1 is associated with the functional fault that the function corresponding to each unit in the initial indenture level obtained in described step 3, each layer indenture level and minimum indenture level and performance requirement kind can occur, and by wherein every two adjacent Level building functional fault hardware matrix figure, thus form multiple functional fault hardware matrix figure; Step 5: failure cause and the fault effects of analyzing each unit in the layer of structure figure in described step 1, and analysis sequence is analysis of going forward one by one from minimum indenture level to initial indenture level direction, wherein, the failure cause of each unit is corresponding with the functional fault hardware matrix figure of this unit in described step 4; The fault effects of each unit is with corresponding to the functional fault of the unit in the upper strata indenture level corresponding to this unit in described step 4.
Preferably, described equipment to be analyzed is airplane equipment.
Present invention also offers a kind of FMEA analytic system of supportability Analysis, for the analytical approach of the FMEA of supportability Analysis as above, it is characterized in that, the FMEA analytic system of described supportability Analysis comprises: AUTOMATIC ZONING unit, described AUTOMATIC ZONING unit is used for equipment to be analyzed to disassemble step by step, thus forms multilayer indenture level; Unit decomposition unit, each layer indenture level that described unit decomposition unit is used for described AUTOMATIC ZONING unit to be formed carries out unit decomposition, thus forms unit, and the unit sum in every layer of indenture level is this layer of indenture level; Structure architectural elements, each layer indenture level that described structure architectural elements is used for AUTOMATIC ZONING unit to obtain combines, thus forms layer of structure figure, wherein, equipment to be analyzed is called initial indenture level, and lowermost level indenture level is called minimum indenture level; Function and performance enumerate unit, and described function and performance enumerate unit for generating the feature list of equipment to be analyzed; Contrast relationship gives unit, and described contrast relationship is given unit and is used for function and performance to enumerate feature list that unit generates and is given to each unit in each indenture level; Analytic unit, each unit that contrast relationship is given in unit by described analytic unit is analyzed, thus the functional fault that the function analyzed corresponding to each unit and performance requirement kind can occur; Associative cell, the functional fault that described associative cell is used for described analytic unit to analyze associates with layer of structure figure, and wherein, the indenture level of any two adjacent levels forms functional fault hardware matrix figure; Logic analysis unit, described logic analysis unit is the initial level of analysis with minimum indenture level, the analysis and go forward one by one in initial indenture level direction, thus analyze failure cause and the fault effects of each unit, and the failure cause of each unit is corresponding with the functional fault hardware matrix figure of this unit in described step 4; The fault effects of each unit is with corresponding to the functional fault of the unit in the upper strata indenture level corresponding to this unit in described step 4; Man-machine interaction unit, described man-machine interaction unit is used for making that operator controls described logic analysis unit, associative cell, analytic unit, contrast relationship are given unit, function and performance and enumerated unit, structure architectural elements, unit decomposition unit and AUTOMATIC ZONING unit.
First the analytical approach of the FMEA of supportability Analysis of the present invention carries out top-down layering from whole this entirety of equipment to be analyzed, and set up functional fault and relation at all levels, afterwards by analysis of going forward one by one from minimum indenture level to initial indenture level direction, thus define a whole set of analytical approach, this analytical approach can solve the failure cause of easily omitting functional fault pattern and correspondence in actual analysis process for the system that level is many existed in prior art, and be not easy when verifying to find to omit, that causes RCMA and corrective maintenance to analyze is imperfect.
Accompanying drawing explanation
Fig. 1 is the schematic flow sheet of the analytical approach of the FMEA of supportability Analysis according to a first embodiment of the present invention.
Fig. 2 is the form schematic diagram of the Aileron control system in the analytical approach of the FMEA of the supportability Analysis shown in Fig. 1 in step 5.
Embodiment
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limiting the scope of the invention.
Fig. 1 is the schematic flow sheet of the analytical approach of the FMEA of supportability Analysis according to a first embodiment of the present invention.
The analytical approach of the FMEA of supportability Analysis as shown in Figure 1 comprises: step 1: equipment to be analyzed is called initial indenture level, this initial indenture level is carried out multilayer decomposition, form multilayer indenture level, and bottom indenture level is called minimum indenture level, produce the layer of structure figure to minimum indenture level from initial indenture level simultaneously, and by each indenture level in layer of structure figure and each minimum indenture level numbering; Wherein, all have in each indenture level and minimum indenture level multiple equipment to be analyzed decompose after unit; Step 2: function and the performance requirement kind of enumerating equipment to be analyzed, and function and the performance requirement kind of giving the corresponding unit of the initial indenture level in the layer of structure figure in step 1, each layer indenture level and minimum indenture level; Step 3: analysis sequence is: from initial indenture level, and go forward one by one to minimum indenture level, analyze the functional fault that the function corresponding to each unit in initial indenture level, each layer indenture level and minimum indenture level and performance requirement kind can occur respectively; Step 4: the layer of structure figure in step 1 is associated with the functional fault that the function corresponding to each unit in the initial indenture level obtained in described step 3, each layer indenture level and minimum indenture level and performance requirement kind can occur, and by wherein every two adjacent Level building functional fault hardware matrix figure, thus form multiple functional fault hardware matrix figure; Step 5: the failure cause of each unit in the layer of structure figure in analytical procedure 1 and fault effects, and analysis sequence is analysis of going forward one by one from minimum indenture level to initial indenture level direction, wherein, the failure cause of each unit is corresponding with the functional fault hardware matrix figure of this unit in step 4; The fault effects of each unit is with corresponding to the functional fault of the unit in the upper strata indenture level corresponding to this unit in step 4.
In the present embodiment, equipment to be analyzed is airplane equipment.Be understandable that, the analytical approach of the FMEA of supportability Analysis of the present invention can be suitable for different mechanical fields, in the present embodiment, is especially applicable to airplane equipment.
By way of example the present invention is further elaborated below.Be understandable that, following citing does not form any limitation of the invention.
Be understandable that, this embodiment is just schematic, and non-fully is illustrated according to the actual framework of aircraft.
For flight control system, according to the method for step 1 of the present invention, thus using flight control system as initial indenture level, and it is decomposed, thus form multilayer indenture level.For the present embodiment, second layer indenture level is respectively:
Aileron control system, rudder control system, elevator-control system and flap control system
Decompose from second layer indenture level, form third layer indenture level, be understandable that, owing to being exemplary embodiment, therefore, in the present embodiment, only divide to third layer indenture level.
For example, Aileron control system continue be decomposed into:
Third layer indenture level (Aileron control system):
Control wheel assembly, driving column assembly, pulley assembly, cable assembly, sector shaft module and rod assembly.
According to step 2 of the present invention, recited function and performance requirement, such as table 1:
Table 1:
According to step 3 of the present invention, analytic function fault, such as table 2 is to table 3:
Table 3:
This citing is owing to only decomposing flight control system, and therefore, when illustrating, only the third layer indenture level of citing flight control system, is understandable that, this third layer indenture level is the minimum indenture level of this citing.
Process in accordance with the present invention 4, obtains functional fault hardware matrix figure, such as, and table 4 and table 5:
Table 4:
Table 5:
Carry out step 5 of the present invention, thus obtain Fig. 2 and table 6.
Table 6:
Present invention also offers a kind of FMEA analytic system of supportability Analysis, for the analytical approach of the FMEA of supportability Analysis as above, the FMEA analytic system of described supportability Analysis comprises:
AUTOMATIC ZONING unit, described AUTOMATIC ZONING unit is used for equipment to be analyzed to disassemble step by step, thus forms multilayer indenture level;
Unit decomposition unit, each layer indenture level that described unit decomposition unit is used for described AUTOMATIC ZONING unit to be formed carries out unit decomposition, thus forms unit, and the unit sum in every layer of indenture level is this layer of indenture level;
Structure architectural elements, each layer indenture level that described structure architectural elements is used for AUTOMATIC ZONING unit to obtain combines, thus forms layer of structure figure, wherein, equipment to be analyzed is called initial indenture level, and lowermost level indenture level is called minimum indenture level;
Function and performance enumerate unit, and described function and performance enumerate unit for generating the feature list of equipment to be analyzed;
Contrast relationship gives unit, and described contrast relationship is given unit and is used for function and performance to enumerate feature list that unit generates and is given to each unit in each indenture level;
Analytic unit, each unit that contrast relationship is given in unit by described analytic unit is analyzed, thus the functional fault that the function analyzed corresponding to each unit and performance requirement kind can occur;
Associative cell, the functional fault that described associative cell is used for described analytic unit to analyze associates with layer of structure figure, and wherein, the indenture level of any two adjacent levels forms functional fault hardware matrix figure;
Logic analysis unit, described logic analysis unit is the initial level of analysis with minimum indenture level, the analysis and go forward one by one in initial indenture level direction, thus analyze failure cause and the fault effects of each unit, and the failure cause of each unit is corresponding with the functional fault hardware matrix figure of this unit in described step 4; The fault effects of each unit is with corresponding to the functional fault of the unit in the upper strata indenture level corresponding to this unit in described step 4;
Man-machine interaction unit, described man-machine interaction unit is used for making that operator controls described logic analysis unit, associative cell, analytic unit, contrast relationship are given unit, function and performance and enumerated unit, structure architectural elements, unit decomposition unit and AUTOMATIC ZONING unit.
In embodiment provided by the present invention, should be understood that disclosed relevant apparatus and method can realize in other way.Such as, device described above is only schematic, such as, the division of described module and unit, be only a kind of logic function to divide, actual can have other dividing mode when realizing, such as multiple unit or assembly can in conjunction with or another system can be integrated into, or some features can be ignored, or do not perform.Another point, shown or discussed coupling each other or direct-coupling or communication connection can be by some interfaces, the indirect coupling of device or unit or communicate overlooking, can be electrically, machinery or other form.
The described unit illustrated as separating component or can may not be and physically separates, and the parts as unit display can yes or no physical location, namely can be positioned at a place, or also can be distributed in multiple network element.Some or all of unit wherein can be selected according to the actual needs to realize the object of the present embodiment scheme.
In addition, each functional unit in an embodiment of the present invention can be integrated in a processing unit, also can be that the independent physics of unit exists, also can two or more unit in a unit integrated.Above-mentioned integrated unit both can adopt the form of hardware to realize, and the form of SFU software functional unit also can be adopted to realize.
If described integrated unit using the form of SFU software functional unit realize and as independently production marketing or use time, can be stored in a computer read/write memory medium, based on such understanding, the part that technical scheme of the present invention contributes to prior art in essence in other words or all or part of of this technical scheme can embody with the form of software product, this computer software product is stored in a storage medium, comprises all or part of step of some instructions in order to make computer processor perform method described in each embodiment of the present invention.And aforesaid storage medium comprise USB flash disk, portable hard drive, ROM (read-only memory), random access memory, magnetic disc or CD etc. various can be program code stored medium.
Finally it is to be noted: above embodiment only in order to technical scheme of the present invention to be described, is not intended to limit.Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (3)
1. an analytical approach of the FMEA of supportability Analysis, is characterized in that for aircraft, and the analytical approach of the FMEA of described supportability Analysis comprises:
Step 1: equipment to be analyzed is called initial indenture level, this initial indenture level is carried out multilayer decomposition, form multilayer indenture level, and bottom indenture level is called minimum indenture level, produce the layer of structure figure to minimum indenture level from initial indenture level simultaneously, and by each indenture level in layer of structure figure and each minimum indenture level numbering; Wherein, all have in each indenture level and minimum indenture level multiple equipment to be analyzed decompose after unit;
Step 2: function and the performance requirement kind of enumerating described equipment to be analyzed, and function and the performance requirement kind of giving the corresponding unit of the initial indenture level in the layer of structure figure in described step 1, each layer indenture level and minimum indenture level;
Step 3: analysis sequence is: from initial indenture level, and go forward one by one to minimum indenture level, analyze the functional fault that the function corresponding to each unit in initial indenture level, each layer indenture level and minimum indenture level and performance requirement kind can occur respectively;
Step 4: the layer of structure figure in described step 1 is associated with the functional fault that the function corresponding to each unit in the initial indenture level obtained in described step 3, each layer indenture level and minimum indenture level and performance requirement kind can occur, and by wherein every two adjacent Level building functional fault hardware matrix figure, thus form multiple functional fault hardware matrix figure;
Step 5: failure cause and the fault effects of analyzing each unit in the layer of structure figure in described step 1, and analysis sequence is analysis of going forward one by one from minimum indenture level to initial indenture level direction, wherein, the failure cause of each unit is corresponding with the functional fault hardware matrix figure of this unit in described step 4; The fault effects of each unit is with corresponding to the functional fault of the unit in the upper strata indenture level corresponding to this unit in described step 4.
2. the analytical approach of the FMEA of supportability Analysis as claimed in claim 1, it is characterized in that, described equipment to be analyzed is airplane equipment.
3. a FMEA analytic system for supportability Analysis, for the analytical approach of the FMEA of supportability Analysis as claimed in claim 1 or 2, is characterized in that, the FMEA analytic system of described supportability Analysis comprises:
AUTOMATIC ZONING unit, described AUTOMATIC ZONING unit is used for equipment to be analyzed to disassemble step by step, thus forms multilayer indenture level;
Unit decomposition unit, each layer indenture level that described unit decomposition unit is used for described AUTOMATIC ZONING unit to be formed carries out unit decomposition, thus forms unit, and the unit sum in every layer of indenture level is this layer of indenture level;
Structure architectural elements, each layer indenture level that described structure architectural elements is used for AUTOMATIC ZONING unit to obtain combines, thus forms layer of structure figure, wherein, equipment to be analyzed is called initial indenture level, and lowermost level indenture level is called minimum indenture level;
Function and performance enumerate unit, and described function and performance enumerate unit for generating the feature list of equipment to be analyzed;
Contrast relationship gives unit, and described contrast relationship is given unit and is used for function and performance to enumerate feature list that unit generates and is given to each unit in each indenture level;
Analytic unit, each unit that contrast relationship is given in unit by described analytic unit is analyzed, thus the functional fault that the function analyzed corresponding to each unit and performance requirement kind can occur;
Associative cell, the functional fault that described associative cell is used for described analytic unit to analyze associates with layer of structure figure, and wherein, the indenture level of any two adjacent levels forms functional fault hardware matrix figure;
Logic analysis unit, described logic analysis unit is the initial level of analysis with minimum indenture level, the analysis and go forward one by one in initial indenture level direction, thus analyze failure cause and the fault effects of each unit, and the failure cause of each unit is corresponding with the functional fault hardware matrix figure of this unit in described step 4; The fault effects of each unit is with corresponding to the functional fault of the unit in the upper strata indenture level corresponding to this unit in described step 4;
Man-machine interaction unit, described man-machine interaction unit is used for making that operator controls described logic analysis unit, associative cell, analytic unit, contrast relationship are given unit, function and performance and enumerated unit, structure architectural elements, unit decomposition unit and AUTOMATIC ZONING unit.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107437116A (en) * | 2017-08-02 | 2017-12-05 | 中国航空工业集团公司西安飞机设计研究所 | It is a kind of towards using and maintenance task Equipment Indemnificatory analysis method |
| CN112051073A (en) * | 2020-08-27 | 2020-12-08 | 安徽江淮汽车集团股份有限公司 | Vehicle transmission resistance measuring method, vehicle transmission resistance measuring system and vehicle transmission resistance measuring storage medium |
| CN112711851A (en) * | 2020-12-29 | 2021-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Fault diagnosis demand data model construction method |
| CN112734058A (en) * | 2020-12-29 | 2021-04-30 | 中国航空工业集团公司西安飞机设计研究所 | Troubleshooting analysis method for aircraft system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102831152A (en) * | 2012-06-28 | 2012-12-19 | 北京航空航天大学 | FMEA (Failure Mode And Effects Analysis) process auxiliary and information management method based on template model and text matching |
| CN103268273A (en) * | 2013-05-24 | 2013-08-28 | 北京航空航天大学 | Failure criterion determination method based on function analysis and mechanism analysis |
| US20130274991A1 (en) * | 2012-04-12 | 2013-10-17 | Airbus Operations (Sas) | Method, devices and program for computer-aided analysis of the failure tolerance of an aircraft system, using critical event charts |
| CN103473400A (en) * | 2013-08-27 | 2013-12-25 | 北京航空航天大学 | Software FMEA (failure mode and effects analysis) method based on level dependency modeling |
| CN104361026A (en) * | 2014-10-22 | 2015-02-18 | 北京航空航天大学 | Failure knowledge storage and push method for FMEA (failure mode and effects analysis) process |
-
2015
- 2015-12-13 CN CN201510932906.1A patent/CN105447266B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130274991A1 (en) * | 2012-04-12 | 2013-10-17 | Airbus Operations (Sas) | Method, devices and program for computer-aided analysis of the failure tolerance of an aircraft system, using critical event charts |
| CN102831152A (en) * | 2012-06-28 | 2012-12-19 | 北京航空航天大学 | FMEA (Failure Mode And Effects Analysis) process auxiliary and information management method based on template model and text matching |
| CN103268273A (en) * | 2013-05-24 | 2013-08-28 | 北京航空航天大学 | Failure criterion determination method based on function analysis and mechanism analysis |
| CN103473400A (en) * | 2013-08-27 | 2013-12-25 | 北京航空航天大学 | Software FMEA (failure mode and effects analysis) method based on level dependency modeling |
| CN104361026A (en) * | 2014-10-22 | 2015-02-18 | 北京航空航天大学 | Failure knowledge storage and push method for FMEA (failure mode and effects analysis) process |
Non-Patent Citations (1)
| Title |
|---|
| 勉力财等: "舰载机多机种一体化保障技术研究", 《 航空装备维修技术及应用研讨会论文集》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107437116A (en) * | 2017-08-02 | 2017-12-05 | 中国航空工业集团公司西安飞机设计研究所 | It is a kind of towards using and maintenance task Equipment Indemnificatory analysis method |
| CN112051073A (en) * | 2020-08-27 | 2020-12-08 | 安徽江淮汽车集团股份有限公司 | Vehicle transmission resistance measuring method, vehicle transmission resistance measuring system and vehicle transmission resistance measuring storage medium |
| CN112051073B (en) * | 2020-08-27 | 2022-03-22 | 安徽江淮汽车集团股份有限公司 | Vehicle transmission resistance measuring method, vehicle transmission resistance measuring system and vehicle transmission resistance measuring storage medium |
| CN112711851A (en) * | 2020-12-29 | 2021-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Fault diagnosis demand data model construction method |
| CN112734058A (en) * | 2020-12-29 | 2021-04-30 | 中国航空工业集团公司西安飞机设计研究所 | Troubleshooting analysis method for aircraft system |
| CN112734058B (en) * | 2020-12-29 | 2023-07-25 | 中国航空工业集团公司西安飞机设计研究所 | Failure analysis method of aircraft system |
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|---|---|
| CN105447266B (en) | 2018-10-09 |
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